Whole-spacecraft vibration isolation system for the GFO/Taurus mission

Conor D. Johnson; Paul S. Wilke; Patrick J. Grosserode

doi:10.1117/12.349780

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2 June 1999 Whole-spacecraft vibration isolation system for the GFO/Taurus mission

Conor D. Johnson, Paul S. Wilke, Patrick J. Grosserode

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Proceedings Volume 3672, Smart Structures and Materials 1999: Passive Damping and Isolation; (1999) https://doi.org/10.1117/12.349780
Event: 1999 Symposium on Smart Structures and Materials, 1999, Newport Beach, CA, United States

Abstract

A whole-spacecraft isolation system for the GFO/Taurus mission was designed, fabricated, tested, and subsequently flown on February 10, 1998. This isolation system was designed to reduce dynamic responses on the GFO spacecraft caused by the resonant burn dynamic load introduced by the Castor 120 solid rocket motor. Longitudinal (flight direction) response of the GFO spacecraft center of gravity, due to the resonant burn load, was reduced by a factor of seven. The isolation system design was very nonintrusive to existing hardware, lightweight, and effective. Flight data indicates that the isolation system performed as designed. The GFO spacecraft had a successful launch and is currently operational on-orbit. A second flight of this type of isolation system occurred in October 1998. Similar isolation systems are planned for other flights in 1999 and 2000. This whole-spacecraft isolation technology was highly successful for the GFO/Taurus mission.

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Conor D. Johnson, Paul S. Wilke, and Patrick J. Grosserode "Whole-spacecraft vibration isolation system for the GFO/Taurus mission", Proc. SPIE 3672, Smart Structures and Materials 1999: Passive Damping and Isolation, (2 June 1999); https://doi.org/10.1117/12.349780

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